/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-
+
Module: FGAuxiliary.cpp
Author: Tony Peden, Jon Berndt
Date started: 01/26/99
Purpose: Calculates additional parameters needed by the visual system, etc.
Called by: FGSimExec
-
+
------------- Copyright (C) 1999 Jon S. Berndt (jsb@hal-pc.org) -------------
-
+
This program is free software; you can redistribute it and/or modify it under
the terms of the GNU General Public License as published by the Free Software
Foundation; either version 2 of the License, or (at your option) any later
version.
-
+
This program is distributed in the hope that it will be useful, but WITHOUT
ANY WARRANTY; without even the implied warranty of MERCHANTABILITY or FITNESS
FOR A PARTICULAR PURPOSE. See the GNU General Public License for more
#include "FGAuxiliary.h"
#include "FGAerodynamics.h"
-#include "FGTranslation.h"
-#include "FGRotation.h"
+#include "FGPropagate.h"
#include "FGAtmosphere.h"
#include "FGState.h"
#include "FGFDMExec.h"
-#include "FGFCS.h"
#include "FGAircraft.h"
-#include "FGPosition.h"
-#include "FGOutput.h"
#include "FGInertial.h"
-#include "FGMatrix33.h"
-#include "FGColumnVector3.h"
-#include "FGColumnVector4.h"
#include "FGPropertyManager.h"
+namespace JSBSim {
+
static const char *IdSrc = "$Id$";
static const char *IdHdr = ID_AUXILIARY;
FGAuxiliary::FGAuxiliary(FGFDMExec* fdmex) : FGModel(fdmex)
{
Name = "FGAuxiliary";
- vcas = veas = mach = qbar = pt = 0;
+ vcas = veas = pt = tat = 0;
psl = rhosl = 1;
earthPosAngle = 0.0;
-
+ qbar = 0;
+ qbarUW = 0.0;
+ qbarUV = 0.0;
+ Mach = 0.0;
+ alpha = beta = 0.0;
+ adot = bdot = 0.0;
+ gamma = Vt = Vground = 0.0;
+ psigt = 0.0;
+ day_of_year = 1;
+ seconds_in_day = 0.0;
+ hoverbmac = hoverbcg = 0.0;
+
+ vPilotAccel.InitMatrix();
vPilotAccelN.InitMatrix();
-
+ vToEyePt.InitMatrix();
+ vAeroPQR.InitMatrix();
+ vEulerRates.InitMatrix();
+
bind();
-
+
Debug(0);
}
bool FGAuxiliary::Run()
{
- double A,B,D;
+ double A,B,D, hdot_Vt;
+ const FGColumnVector3& vPQR = Propagate->GetPQR();
+ const FGColumnVector3& vUVW = Propagate->GetUVW();
+ const FGColumnVector3& vUVWdot = Propagate->GetUVWdot();
+ const FGColumnVector3& vVel = Propagate->GetVel();
+
+ if (!FGModel::Run())
+ {
+ p = Atmosphere->GetPressure();
+ rhosl = Atmosphere->GetDensitySL();
+ psl = Atmosphere->GetPressureSL();
+ sat = Atmosphere->GetTemperature();
+
+// Rotation
+
+ double cTht = Propagate->GetCosEuler(eTht);
+ double cPhi = Propagate->GetCosEuler(ePhi);
+ double sPhi = Propagate->GetSinEuler(ePhi);
+
+ vEulerRates(eTht) = vPQR(eQ)*cPhi - vPQR(eR)*sPhi;
+ if (cTht != 0.0) {
+ vEulerRates(ePsi) = (vPQR(eQ)*sPhi + vPQR(eR)*cPhi)/cTht;
+ vEulerRates(ePhi) = vPQR(eP) + vEulerRates(ePsi)*sPhi;
+ }
- if (!FGModel::Run()) {
- GetState();
- if (mach < 1) { //calculate total pressure assuming isentropic flow
- pt=p*pow((1 + 0.2*mach*mach),3.5);
+ vAeroPQR = vPQR + Atmosphere->GetTurbPQR();
+
+// Translation
+
+ vAeroUVW = vUVW + Propagate->GetTl2b()*Atmosphere->GetWindNED();
+
+ Vt = vAeroUVW.Magnitude();
+ if ( Vt > 0.05) {
+ if (vAeroUVW(eW) != 0.0)
+ alpha = vAeroUVW(eU)*vAeroUVW(eU) > 0.0 ? atan2(vAeroUVW(eW), vAeroUVW(eU)) : 0.0;
+ if (vAeroUVW(eV) != 0.0)
+ beta = vAeroUVW(eU)*vAeroUVW(eU)+vAeroUVW(eW)*vAeroUVW(eW) > 0.0 ? atan2(vAeroUVW(eV),
+ sqrt(vAeroUVW(eU)*vAeroUVW(eU) + vAeroUVW(eW)*vAeroUVW(eW))) : 0.0;
+
+ double mUW = (vAeroUVW(eU)*vAeroUVW(eU) + vAeroUVW(eW)*vAeroUVW(eW));
+ double signU=1;
+ if (vAeroUVW(eU) != 0.0)
+ signU = vAeroUVW(eU)/fabs(vAeroUVW(eU));
+
+ if ( (mUW == 0.0) || (Vt == 0.0) ) {
+ adot = 0.0;
+ bdot = 0.0;
+ } else {
+ adot = (vAeroUVW(eU)*vUVWdot(eW) - vAeroUVW(eW)*vUVWdot(eU))/mUW;
+ bdot = (signU*mUW*vUVWdot(eV) - vAeroUVW(eV)*(vAeroUVW(eU)*vUVWdot(eU)
+ + vAeroUVW(eW)*vUVWdot(eW)))/(Vt*Vt*sqrt(mUW));
+ }
} else {
- // shock in front of pitot tube, we'll assume its normal and use
- // the Rayleigh Pitot Tube Formula, i.e. the ratio of total
- // pressure behind the shock to the static pressure in front
+ alpha = beta = adot = bdot = 0;
+ }
- B = 5.76*mach*mach/(5.6*mach*mach - 0.8);
+ qbar = 0.5*Atmosphere->GetDensity()*Vt*Vt;
+ qbarUW = 0.5*Atmosphere->GetDensity()*(vAeroUVW(eU)*vAeroUVW(eU) + vAeroUVW(eW)*vAeroUVW(eW));
+ qbarUV = 0.5*Atmosphere->GetDensity()*(vAeroUVW(eU)*vAeroUVW(eU) + vAeroUVW(eV)*vAeroUVW(eV));
+ Mach = Vt / Atmosphere->GetSoundSpeed();
+ MachU = vMachUVW(eU) = vAeroUVW(eU) / Atmosphere->GetSoundSpeed();
+ vMachUVW(eV) = vAeroUVW(eV) / Atmosphere->GetSoundSpeed();
+ vMachUVW(eW) = vAeroUVW(eW) / Atmosphere->GetSoundSpeed();
- // The denominator above is zero for Mach ~ 0.38, for which
- // we'll never be here, so we're safe
+// Position
- D = (2.8*mach*mach-0.4)*0.4167;
+ Vground = sqrt( vVel(eNorth)*vVel(eNorth) + vVel(eEast)*vVel(eEast) );
+
+ if (vVel(eNorth) == 0) psigt = 0;
+ else psigt = atan2(vVel(eEast), vVel(eNorth));
+
+ if (psigt < 0.0) psigt += 2*M_PI;
+
+ if (Vt != 0) {
+ hdot_Vt = -vVel(eDown)/Vt;
+ if (fabs(hdot_Vt) <= 1) gamma = asin(hdot_Vt);
+ } else {
+ gamma = 0.0;
+ }
+
+ tat = sat*(1 + 0.2*Mach*Mach); // Total Temperature, isentropic flow
+ tatc = RankineToCelsius(tat);
+
+ if (MachU < 1) { // Calculate total pressure assuming isentropic flow
+ pt = p*pow((1 + 0.2*MachU*MachU),3.5);
+ } else {
+ // Use Rayleigh pitot tube formula for normal shock in front of pitot tube
+ B = 5.76*MachU*MachU/(5.6*MachU*MachU - 0.8);
+ D = (2.8*MachU*MachU-0.4)*0.4167;
pt = p*pow(B,3.5)*D;
}
A = pow(((pt-p)/psl+1),0.28571);
- vcas = sqrt(7*psl/rhosl*(A-1));
- veas = sqrt(2*qbar/rhosl);
-
- // Pilot sensed accelerations are calculated here. This is used
- // for the coordinated turn ball instrument. Motion base platforms sometimes
- // use the derivative of pilot sensed accelerations as the driving parameter,
- // rather than straight accelerations.
- //
- // The theory behind pilot-sensed calculations is presented:
- //
- // For purposes of discussion and calculation, assume for a minute that the
- // pilot is in space and motionless in inertial space. She will feel
- // no accelerations. If the aircraft begins to accelerate along any axis or
- // axes (without rotating), the pilot will sense those accelerations. If
- // any rotational moment is applied, the pilot will sense an acceleration
- // due to that motion in the amount:
- //
- // [wdot X R] + [w X (w X R)]
- // Term I Term II
- //
- // where:
- //
- // wdot = omegadot, the rotational acceleration rate vector
- // w = omega, the rotational rate vector
- // R = the vector from the aircraft CG to the pilot eyepoint
- //
- // The sum total of these two terms plus the acceleration of the aircraft
- // body axis gives the acceleration the pilot senses in inertial space.
- // In the presence of a large body such as a planet, a gravity field also
- // provides an accelerating attraction. This acceleration can be transformed
- // from the reference frame of the planet so as to be expressed in the frame
- // of reference of the aircraft. This gravity field accelerating attraction
- // is felt by the pilot as a force on her tushie as she sits in her aircraft
- // on the runway awaiting takeoff clearance.
- //
- // In JSBSim the acceleration of the body frame in inertial space is given
- // by the F = ma relation. If the vForces vector is divided by the aircraft
- // mass, the acceleration vector is calculated. The term wdot is equivalent
- // to the JSBSim vPQRdot vector, and the w parameter is equivalent to vPQR.
- // The radius R is calculated below in the vector vToEyePt.
-
- vPilotAccel.InitMatrix();
- if ( Translation->GetVt() > 1 ) {
- vToEyePt = Aircraft->GetXYZep() - MassBalance->GetXYZcg();
- vToEyePt *= inchtoft;
- vPilotAccel = Aerodynamics->GetForces()
- + Propulsion->GetForces()
- + GroundReactions->GetForces();
- vPilotAccel /= MassBalance->GetMass();
- vPilotAccel += Rotation->GetPQRdot() * vToEyePt;
- vPilotAccel += Rotation->GetPQR() * (Rotation->GetPQR() * vToEyePt);
- //vPilotAccel(2)*=-1;
- vPilotAccelN = vPilotAccel/Inertial->gravity();
+ if (MachU > 0.0) {
+ vcas = sqrt(7*psl/rhosl*(A-1));
+ veas = sqrt(2*qbar/rhosl);
+ } else {
+ vcas = veas = 0.0;
+ }
+
+ vPilotAccel.InitMatrix();
+ if ( Vt > 1.0 ) {
+ vPilotAccel = Aerodynamics->GetForces()
+ + Propulsion->GetForces()
+ + GroundReactions->GetForces();
+ vPilotAccel /= MassBalance->GetMass();
+ vToEyePt = MassBalance->StructuralToBody(Aircraft->GetXYZep());
+ vPilotAccel += Propagate->GetPQRdot() * vToEyePt;
+ vPilotAccel += vPQR * (vPQR * vToEyePt);
+ } else {
+ vPilotAccel = Propagate->GetTl2b() * FGColumnVector3( 0.0, 0.0, Inertial->gravity() );
}
+
+ vPilotAccelN = vPilotAccel/Inertial->gravity();
+
earthPosAngle += State->Getdt()*Inertial->omega();
+
+ // VRP computation
+ const FGLocation& vLocation = Propagate->GetLocation();
+ FGColumnVector3 vrpStructural = Aircraft->GetXYZvrp();
+ FGColumnVector3 vrpBody = MassBalance->StructuralToBody( vrpStructural );
+ FGColumnVector3 vrpLocal = Propagate->GetTb2l() * vrpBody;
+ vLocationVRP = vLocation.LocalToLocation( vrpLocal );
+
+ // Recompute some derived values now that we know the dependent parameters values ...
+ hoverbcg = Propagate->GetDistanceAGL() / Aircraft->GetWingSpan();
+
+ FGColumnVector3 vMac = Propagate->GetTb2l()*MassBalance->StructuralToBody(Aircraft->GetXYZrp());
+ hoverbmac = (Propagate->GetDistanceAGL() + vMac(3)) / Aircraft->GetWingSpan();
+
return false;
} else {
return true;
double FGAuxiliary::GetHeadWind(void)
{
- double psiw,vw,psi;
+ double psiw,vw;
psiw = Atmosphere->GetWindPsi();
- psi = Rotation->Getpsi();
vw = Atmosphere->GetWindNED().Magnitude();
- return vw*cos(psiw - psi);
+ return vw*cos(psiw - Propagate->GetEuler(ePsi));
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
double FGAuxiliary::GetCrossWind(void)
{
- double psiw,vw,psi;
+ double psiw,vw;
psiw = Atmosphere->GetWindPsi();
- psi = Rotation->Getpsi();
vw = Atmosphere->GetWindNED().Magnitude();
- return vw*sin(psiw - psi);
+ return vw*sin(psiw - Propagate->GetEuler(ePsi));
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
void FGAuxiliary::bind(void)
{
typedef double (FGAuxiliary::*PMF)(int) const;
- PropertyManager->Tie("velocities/vc-fps", this,
- &FGAuxiliary::GetVcalibratedFPS);
- PropertyManager->Tie("velocities/vc-kts", this,
- &FGAuxiliary::GetVcalibratedKTS);
- PropertyManager->Tie("velocities/ve-fps", this,
- &FGAuxiliary::GetVequivalentFPS);
- PropertyManager->Tie("velocities/ve-kts", this,
- &FGAuxiliary::GetVequivalentKTS);
- PropertyManager->Tie("accelerations/a-pilot-x-ft_sec2", this,1,
- (PMF)&FGAuxiliary::GetPilotAccel);
- PropertyManager->Tie("accelerations/a-pilot-y-ft_sec2", this,2,
- (PMF)&FGAuxiliary::GetPilotAccel);
- PropertyManager->Tie("accelerations/a-pilot-z-ft_sec2", this,3,
- (PMF)&FGAuxiliary::GetPilotAccel);
- PropertyManager->Tie("accelerations/n-pilot-x-norm", this,1,
- (PMF)&FGAuxiliary::GetNpilot);
- PropertyManager->Tie("accelerations/n-pilot-y-norm", this,2,
- (PMF)&FGAuxiliary::GetNpilot);
- PropertyManager->Tie("accelerations/n-pilot-z-norm", this,3,
- (PMF)&FGAuxiliary::GetNpilot);
- PropertyManager->Tie("position/epa-rad", this,
- &FGAuxiliary::GetEarthPositionAngle);
- /* PropertyManager->Tie("atmosphere/headwind-fps", this,
- &FGAuxiliary::GetHeadWind,
- true);
- PropertyManager->Tie("atmosphere/crosswind-fps", this,
- &FGAuxiliary::GetCrossWind,
- true); */
+ typedef double (FGAuxiliary::*PF)(void) const;
+ PropertyManager->Tie("velocities/vc-fps", this, &FGAuxiliary::GetVcalibratedFPS);
+ PropertyManager->Tie("velocities/vc-kts", this, &FGAuxiliary::GetVcalibratedKTS);
+ PropertyManager->Tie("velocities/ve-fps", this, &FGAuxiliary::GetVequivalentFPS);
+ PropertyManager->Tie("velocities/ve-kts", this, &FGAuxiliary::GetVequivalentKTS);
+ PropertyManager->Tie("velocities/machU", this, &FGAuxiliary::GetMachU);
+ PropertyManager->Tie("velocities/tat-r", this, &FGAuxiliary::GetTotalTemperature);
+ PropertyManager->Tie("velocities/tat-c", this, &FGAuxiliary::GetTAT_C);
+ PropertyManager->Tie("velocities/pt-lbs_sqft", this, &FGAuxiliary::GetTotalPressure);
+ PropertyManager->Tie("velocities/p-aero-rad_sec", this, eX, (PMF)&FGAuxiliary::GetAeroPQR);
+ PropertyManager->Tie("velocities/q-aero-rad_sec", this, eY, (PMF)&FGAuxiliary::GetAeroPQR);
+ PropertyManager->Tie("velocities/r-aero-rad_sec", this, eZ, (PMF)&FGAuxiliary::GetAeroPQR);
+ PropertyManager->Tie("velocities/phidot-rad_sec", this, ePhi, (PMF)&FGAuxiliary::GetEulerRates);
+ PropertyManager->Tie("velocities/thetadot-rad_sec", this, eTht, (PMF)&FGAuxiliary::GetEulerRates);
+ PropertyManager->Tie("velocities/psidot-rad_sec", this, ePsi, (PMF)&FGAuxiliary::GetEulerRates);
+ PropertyManager->Tie("velocities/u-aero-fps", this, eU, (PMF)&FGAuxiliary::GetAeroUVW);
+ PropertyManager->Tie("velocities/v-aero-fps", this, eV, (PMF)&FGAuxiliary::GetAeroUVW);
+ PropertyManager->Tie("velocities/w-aero-fps", this, eW, (PMF)&FGAuxiliary::GetAeroUVW);
+ PropertyManager->Tie("velocities/vt-fps", this, &FGAuxiliary::GetVt, &FGAuxiliary::SetVt, true);
+ PropertyManager->Tie("velocities/mach-norm", this, &FGAuxiliary::GetMach, &FGAuxiliary::SetMach, true);
+ PropertyManager->Tie("velocities/vg-fps", this, &FGAuxiliary::GetVground);
+ PropertyManager->Tie("accelerations/a-pilot-x-ft_sec2", this, eX, (PMF)&FGAuxiliary::GetPilotAccel);
+ PropertyManager->Tie("accelerations/a-pilot-y-ft_sec2", this, eY, (PMF)&FGAuxiliary::GetPilotAccel);
+ PropertyManager->Tie("accelerations/a-pilot-z-ft_sec2", this, eZ, (PMF)&FGAuxiliary::GetPilotAccel);
+ PropertyManager->Tie("accelerations/n-pilot-x-norm", this, eX, (PMF)&FGAuxiliary::GetNpilot);
+ PropertyManager->Tie("accelerations/n-pilot-y-norm", this, eY, (PMF)&FGAuxiliary::GetNpilot);
+ PropertyManager->Tie("accelerations/n-pilot-z-norm", this, eZ, (PMF)&FGAuxiliary::GetNpilot);
+ PropertyManager->Tie("position/epa-rad", this, &FGAuxiliary::GetEarthPositionAngle);
+ /* PropertyManager->Tie("atmosphere/headwind-fps", this, &FGAuxiliary::GetHeadWind, true);
+ PropertyManager->Tie("atmosphere/crosswind-fps", this, &FGAuxiliary::GetCrossWind, true); */
+ PropertyManager->Tie("aero/alpha-rad", this, (PF)&FGAuxiliary::Getalpha, &FGAuxiliary::Setalpha, true);
+ PropertyManager->Tie("aero/beta-rad", this, (PF)&FGAuxiliary::Getbeta, &FGAuxiliary::Setbeta, true);
+ PropertyManager->Tie("aero/mag-beta-rad", this, (PF)&FGAuxiliary::GetMagBeta);
+ PropertyManager->Tie("aero/alpha-deg", this, inDegrees, (PMF)&FGAuxiliary::Getalpha);
+ PropertyManager->Tie("aero/beta-deg", this, inDegrees, (PMF)&FGAuxiliary::Getbeta);
+ PropertyManager->Tie("aero/mag-beta-deg", this, inDegrees, (PMF)&FGAuxiliary::GetMagBeta);
+ PropertyManager->Tie("aero/qbar-psf", this, &FGAuxiliary::Getqbar, &FGAuxiliary::Setqbar, true);
+ PropertyManager->Tie("aero/qbarUW-psf", this, &FGAuxiliary::GetqbarUW, &FGAuxiliary::SetqbarUW, true);
+ PropertyManager->Tie("aero/qbarUV-psf", this, &FGAuxiliary::GetqbarUV, &FGAuxiliary::SetqbarUV, true);
+ PropertyManager->Tie("aero/alphadot-rad_sec", this, (PF)&FGAuxiliary::Getadot, &FGAuxiliary::Setadot, true);
+ PropertyManager->Tie("aero/betadot-rad_sec", this, (PF)&FGAuxiliary::Getbdot, &FGAuxiliary::Setbdot, true);
+ PropertyManager->Tie("aero/alphadot-deg_sec", this, inDegrees, (PMF)&FGAuxiliary::Getadot);
+ PropertyManager->Tie("aero/betadot-deg_sec", this, inDegrees, (PMF)&FGAuxiliary::Getbdot);
+ PropertyManager->Tie("aero/h_b-cg-ft", this, &FGAuxiliary::GetHOverBCG);
+ PropertyManager->Tie("aero/h_b-mac-ft", this, &FGAuxiliary::GetHOverBMAC);
+ PropertyManager->Tie("flight-path/gamma-rad", this, &FGAuxiliary::GetGamma, &FGAuxiliary::SetGamma);
+ PropertyManager->Tie("flight-path/psi-gt-rad", this, &FGAuxiliary::GetGroundTrack);
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
PropertyManager->Untie("velocities/vc-kts");
PropertyManager->Untie("velocities/ve-fps");
PropertyManager->Untie("velocities/ve-kts");
+ PropertyManager->Untie("velocities/machU");
+ PropertyManager->Untie("velocities/tat-r");
+ PropertyManager->Untie("velocities/tat-c");
+ PropertyManager->Untie("velocities/p-aero-rad_sec");
+ PropertyManager->Untie("velocities/q-aero-rad_sec");
+ PropertyManager->Untie("velocities/r-aero-rad_sec");
+ PropertyManager->Untie("velocities/pt-lbs_sqft");
+ PropertyManager->Untie("velocities/phidot-rad_sec");
+ PropertyManager->Untie("velocities/thetadot-rad_sec");
+ PropertyManager->Untie("velocities/psidot-rad_sec");
+ PropertyManager->Untie("velocities/u-aero-fps");
+ PropertyManager->Untie("velocities/v-aero-fps");
+ PropertyManager->Untie("velocities/w-aero-fps");
+ PropertyManager->Untie("velocities/vt-fps");
+ PropertyManager->Untie("velocities/mach-norm");
+ PropertyManager->Untie("velocities/vg-fps");
PropertyManager->Untie("accelerations/a-pilot-x-ft_sec2");
PropertyManager->Untie("accelerations/a-pilot-y-ft_sec2");
PropertyManager->Untie("accelerations/a-pilot-z-ft_sec2");
PropertyManager->Untie("position/epa-rad");
/* PropertyManager->Untie("atmosphere/headwind-fps");
PropertyManager->Untie("atmosphere/crosswind-fps"); */
-
-}
-
-//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-
-void FGAuxiliary::GetState(void)
-{
- qbar = Translation->Getqbar();
- mach = Translation->GetMach();
- p = Atmosphere->GetPressure();
- rhosl = Atmosphere->GetDensitySL();
- psl = Atmosphere->GetPressureSL();
+ PropertyManager->Untie("aero/qbar-psf");
+ PropertyManager->Untie("aero/qbarUW-psf");
+ PropertyManager->Untie("aero/qbarUV-psf");
+ PropertyManager->Untie("aero/alpha-rad");
+ PropertyManager->Untie("aero/beta-rad");
+ PropertyManager->Untie("aero/alpha-deg");
+ PropertyManager->Untie("aero/beta-deg");
+ PropertyManager->Untie("aero/alphadot-rad_sec");
+ PropertyManager->Untie("aero/betadot-rad_sec");
+ PropertyManager->Untie("aero/mag-beta-rad");
+ PropertyManager->Untie("aero/alphadot-deg_sec");
+ PropertyManager->Untie("aero/betadot-deg_sec");
+ PropertyManager->Untie("aero/mag-beta-deg");
+ PropertyManager->Untie("aero/h_b-cg-ft");
+ PropertyManager->Untie("aero/h_b-mac-ft");
+ PropertyManager->Untie("flight-path/gamma-rad");
+ PropertyManager->Untie("flight-path/psi-gt-rad");
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
if (debug_lvl & 8 ) { // Runtime state variables
}
if (debug_lvl & 16) { // Sanity checking
+ if (Mach > 100 || Mach < 0.00)
+ cout << "FGPropagate::Mach is out of bounds: " << Mach << endl;
+ if (qbar > 1e6 || qbar < 0.00)
+ cout << "FGPropagate::qbar is out of bounds: " << qbar << endl;
}
if (debug_lvl & 64) {
if (from == 0) { // Constructor
}
}
+} // namespace JSBSim
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